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A critical analysis of the accuracy of several numerical techniques for combustion kinetic rate equationsA detailed analysis of the accuracy of several techniques recently developed for integrating stiff ordinary differential equations is presented. The techniques include two general-purpose codes EPISODE and LSODE developed for an arbitrary system of ordinary differential equations, and three specialized codes CHEMEQ, CREK1D, and GCKP4 developed specifically to solve chemical kinetic rate equations. The accuracy study is made by application of these codes to two practical combustion kinetics problems. Both problems describe adiabatic, homogeneous, gas-phase chemical reactions at constant pressure, and include all three combustion regimes: induction, heat release, and equilibration. To illustrate the error variation in the different combustion regimes the species are divided into three types (reactants, intermediates, and products), and error versus time plots are presented for each species type and the temperature. These plots show that CHEMEQ is the most accurate code during induction and early heat release. During late heat release and equilibration, however, the other codes are more accurate. A single global quantity, a mean integrated root-mean-square error, that measures the average error incurred in solving the complete problem is used to compare the accuracy of the codes. Among the codes examined, LSODE is the most accurate for solving chemical kinetics problems. It is also the most efficient code, in the sense that it requires the least computational work to attain a specified accuracy level. An important finding is that use of the algebraic enthalpy conservation equation to compute the temperature can be more accurate and efficient than integrating the temperature differential equation.
Document ID
19930007752
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Radhadrishnan, Krishnan
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1993
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.60:3315
E-5861
NASA-TP-3315
Report Number: NAS 1.60:3315
Report Number: E-5861
Report Number: NASA-TP-3315
Accession Number
93N16941
Funding Number(s)
PROJECT: RTOP 505-31-42
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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